An aerospace component may comprise a fiber reinforced composite material. The fiber reinforced composite material includes a plurality of fiber layers and a carbon matrix surrounding the plurality of fiber layers. A plurality of ceramic particles is dispersed in the carbon matrix. A first fiber layer of the plurality of fiber layers may include a carbon fiber, and a second fiber layer of the plurality of fiber layers may include a non-carbon fiber. A hardness of the non-carbon fiber is greater than a hardness of carbon fiber.

A component for use in a semiconductor processing chamber is provided. A component body of a dielectric material has a semiconductor processing facing surface. A coating of a dielectric material is on at least the semiconductor processing facing surface, wherein the dielectric material of the component body has a same stoichiometry as the dielectric material of the coating.

A method of forming a ceramic matrix composite component. The ceramic matrix composite component is adapted for use in a gas turbine engine. The method including forming the component using ceramic materials and infiltrating the component with a matrix material.

Disclosed herein is a dual density disc comprising a dense outer tube comprising alumina having a purity of greater than 99%; and a porous core comprising alumina of a lower density than a density of the dense outer tube; wherein the porous core has an alumina purity of greater than 99%. Disclosed herein too is method comprising disposing in a dense outer tube a slurry comprising alumina powder and a pore former; heating the dense outer tube with the slurry disposed therein to a temperature of 300 to 600° C. to activate the pore former; creating a porous core in the dense outer tube; and sintering the dense outer tube with the porous core at a temperature of 800 to 2000° C. in one or more stages.

Disclosed herein is a dual density disc comprising a dense outer tube comprising a metal oxide having a purity of greater than 92%; and a porous core comprising a metal oxide of a lower density than a density of the dense outer tube; wherein the porous core has a metal oxide purity of greater than 99%; where the dense outer tube has an inner tapered surface.

Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

A ceramic fiber preform includes a plurality of ceramic fiber plies arranged to define a wall, a void adjacent the wall, and an insert positioned within the void. The insert includes a first region having a first porosity and a second region in physical contact with the first region and having a second porosity. The first region and second region are formed from a woven ceramic material, the wall has a wall porosity, and the first porosity is less than at least one of the second porosity and the wall porosity.

A method of preparing a ceramic fabric and ceramic matrix composite components constructed from the ceramic fabric include transforming ceramic tows, or ceramic fabrics, to varying degrees from a first tow geometry to a second tow geometry, thereby reducing a first dimension of the ceramic tows and increasing a second dimension of the ceramic tows orthogonal to the first dimension. Plies constructed with flattened tows, or as-received tows, have various inter-tow pore sizes that are arranged with increasing inter-tow pore size towards exterior surfaces of the preform structure.

A method for producing a ceramic matrix composite component is disclosed. The method includes providing a plurality of first ceramic fiber plies including a plurality of interconnected tows and a plurality of first pores positioned between adjacent tows. The method includes applying a plurality of first ceramic particles within the plurality of first pores. Next, the method includes applying a plurality of second ceramic fiber plies onto an outer surface of the plurality of first ceramic fiber plies. The second ceramic fiber plies include a plurality of interconnected tows and a plurality of second pores positioned between adjacent tows. The method then includes applying a plurality of second ceramic particles within the plurality of second pores. Further, the plurality of second ceramic particles are larger than the plurality of first ceramic particles. Lastly, the method includes densifying the ceramic matrix composite preform to form the ceramic matrix composite component.

A gas inlet suitable in particular for use in an ion thruster includes a housing which is made of a gas-tight ceramics material, and an insert which is arranged in the housing and is made of a porous ceramics material. The geometry and pore structure of the insert are such that the insert forms a desired flow resistance for a gas stream flowing through the insert.